Simulacija dozvučnog leta modernog lovačkog zrakoplova

master's thesis

• Title (english): Subsonic flight simulation for modern fighter aircraft
• Author: Matej Kos
• Mentor: Milan Vrdoljak (mentor)
• Granter: University of Zagreb; Faculty of Mechanical Engineering and Naval Architecture; Zagreb
• Defense date and country: 2022-01-19, Croatia
• Scientific / art field, discipline and subdiscipline: TECHNICAL SCIENCES; Aviation, Rocket and Space Technology

Abstract

U radu je promatran moderni lovački zrakoplov kanard-krilo konfiguracije, nalik na Dassault Rafale. Prikazane su osnovne geometrijske značajke zrakoplova te su na temelju sličnih zrakoplova procijenjene njegove inercijske značajke. Za aeroprofil krila i stabilizacijskih površina pretpostavljen je bikonveksni aeroprofil relativne debljine 7%, odnosno 5%. Aerodinamičke karakteristike promatranog zrakoplova procijenjene su metodama projektne aerodinamike, dok je pogonska sila zrakoplova modelirana na temelju dostupnih podataka i sličnih motora. Analizirana je statička stabilnost zrakoplova, a za analizu dinamičke stabilnosti primjenjen je linearni model gibanja. Predloženi su osnovni sustavi stabilizacije zrakoplova, a root locus metodom dobivena su pojačanja svih potrebnih povratnih veza. Svi dobiveni rezultati implementirani su u Simulink okruženje u model leta sa šest stupnjeva slobode gibanja. Konačno, analiziran je primjer simulacije leta s dva različita sustava upravljanja, odnosno sa sustavom upravljanja stavom i sa sustavom upravljanja kutnom brzinom.

Abstract (english)

This thesis deals with the analysis of canard-wing configuration modern jet fighter, as is Dassault Rafale. Firstly, basic aircraft information are shown, and based on similar aircraft, its inertial characteristics are calculated. Biconvex airfoil was assumed to be wing and stabilizer airfoil with the relative thickness of 7% and 5%, respectively. Aircraft aerodynamic characteristics were calculated using handbook aerodynamic methods, while aircraft thrust was modeled based on available data and similar jet engines. Furthermore, aircraft static stability was analyzed and a linearized model was used to analyze aircraft dynamic stability. Basic stability augmentation systems were proposed whose feedback gains were chosen based on a root locus analysis. The 6DOF flight model was implemented into Simulink. Finally, a couple of flight simulations were shown with two distinct flight control systems, attitude control system and pitch rate control system.

• Keywords: Kanard-krilo konfiguracija; bikonveksni aeroprofil; stabilnost zrakoplova; sustavi stabilizacije; 6DOF; sustavi upravljanja
• Keywords (english): Canard-wing configuration; biconvex airfoil; aircraft stability; stability augmentation systems; 6DOF; flight control systems
• Language: croatian
• URN:NBN: urn:nbn:hr:235:849032
• Study programme: Title: Aeronautical Studies; Study programme type: university; Study level: graduate; Academic / professional title: magistar/magistra inženjer/inženjerka zrakoplovnog inženjerstva (magistar/magistra inženjer/inženjerka zrakoplovnog inženjerstva)
• Type of resource: Text
• File origin: Born digital
• Access conditions: Open access
• Created on: 2022-01-18 13:33:49